CN106337739B - It is used to support the bearing assembly of the armature spindle of gas-turbine unit - Google Patents
It is used to support the bearing assembly of the armature spindle of gas-turbine unit Download PDFInfo
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- CN106337739B CN106337739B CN201610535029.9A CN201610535029A CN106337739B CN 106337739 B CN106337739 B CN 106337739B CN 201610535029 A CN201610535029 A CN 201610535029A CN 106337739 B CN106337739 B CN 106337739B
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- bearing
- outer cover
- spring arm
- supporting element
- radially
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
- F01D25/164—Flexible supports; Vibration damping means associated with the bearing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/027—Arrangements for balancing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C27/00—Elastic or yielding bearings or bearing supports, for exclusively rotary movement
- F16C27/04—Ball or roller bearings, e.g. with resilient rolling bodies
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
- F16C33/30—Parts of ball or roller bearings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C35/00—Rigid support of bearing units; Housings, e.g. caps, covers
- F16C35/04—Rigid support of bearing units; Housings, e.g. caps, covers in the case of ball or roller bearings
- F16C35/06—Mounting or dismounting of ball or roller bearings; Fixing them onto shaft or in housing
- F16C35/07—Fixing them on the shaft or housing with interposition of an element
- F16C35/073—Fixing them on the shaft or housing with interposition of an element between shaft and inner race ring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/24—Rotors for turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/50—Bearings
- F05D2240/52—Axial thrust bearings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/60—Shafts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C19/00—Bearings with rolling contact, for exclusively rotary movement
- F16C19/02—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows
- F16C19/14—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load
- F16C19/16—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with a single row of balls
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2360/00—Engines or pumps
- F16C2360/23—Gas turbine engines
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Support Of The Bearing (AREA)
- Mounting Of Bearings Or Others (AREA)
- Rolling Contact Bearings (AREA)
Abstract
The present invention relates to the bearing assemblies for the armature spindle for being used to support gas-turbine unit.In an aspect, bearing assembly (100) for support construction (108) support armature spindle (106) relative to gas-turbine unit (10) can generally include bearing (112), outer bearing outer cover (102) and inner bearing supporting element (104), bearing includes outer race (116) and inside race (114), outer bearing outer cover is configured between the outer race of bearing and the support construction of gas-turbine unit radially, inner bearing support configuration between the inside race and armature spindle of bearing radially.Furthermore, outer bearing outer cover and inner bearing supporting element respectively include at least one spring arm (138,164) radially, so that outer bearing outer cover and inner bearing supporting element are collectively form two springs, the two springs are serially linked between support construction and armature spindle.
Description
Technical field
This theme relates generally to gas-turbine unit, and more specifically, is related to being used to support gas turbine and start
The bearing assembly of the armature spindle of machine.
Background technique
Gas-turbine unit generally includes rotor assembly, compressor and turbine.Rotor assembly includes fan, the fan
With the fan blade array to extend radially outwardly from armature spindle.Power and rotary motion are transferred to compression from turbine by armature spindle
Both machine and fan, and be longitudinally supported using multiple bearing assemblies.In addition, rotor assembly has rotation axis, the rotation
Shaft axis passes through rotor c.g..Known bearing assembly includes rolling element and with counter race, wherein rolling element is supported on
With in counter race (paired race).In order to maintain critical rotor speed nargin, rotor assembly is usually supported at three bearings
On component, one of those is thrust bearing assembly, and two therein are roller bearing components.Thrust bearing assembly support turns
Sub- axis, and minimize the axially and radially mobile of rotor shaft assembly.Remaining roller bearing component supports the radial direction of armature spindle
It is mobile.
During the operation of engine, the segment of fan blade can be separated from the rest part of blade.Therefore, significant uneven
The rotary load of weighing apparatus can be formed in the fan of damage, and must be substantially by fan shaft bearing, fan spindle bearing supporting element and wind
Braced frame is fanned to carry.
In order to make may the influence of the abnormal unbalanced load of damage minimize, it is known that gas-turbine unit include using
In the supporting member of fan propeller support system, they are set as providing additional intensity in terms of size.However, working as engine
When operating in the case where not significant rotor unbalance, the intensity for improving supporting member undesirably increases the total of engine
Weight, and reduce the gross efficiency of engine.
Other known engine includes bearing supports, which includes the section mechanically weakened or main guarantor
Dangerous part (primary fuse) disconnects fan propeller from fan support system and couples.During such event, fan shaft is sought
The rotation center looked for novelty, the new rotation center is close to its unbalanced center of gravity.The safety piece section and rotor clearance tolerance group
It closes ground and is known as load reduction device or LRD.LRD reduces the rotation dynamic load in fan support system.
After the destruction of main safety piece, inclined fan propeller usually causes big torque to next nearest bearing.?
In many constructions, it is known that next nearest bearing is second bearing position.To torque caused by second bearing to fan propeller office
Cause to portion high bending and shear-loaded.In order to mitigate shearing force, usually weaken or reduce the radial direction of second bearing position
Rigidity.However, in order to adapt to the axial load transmitted across engine, second bearing supporting element must also provide high axial rigid
Degree.
Existing bearing assembly can be used for providing the radial rigidity of decrease, while provide axial rigidity sufficiently high.However,
It is quantitative and when the thermal efficiency increases in the bypass of modern gas turbine engines, across the transmission of such engine resulting axial direction with
Radial load accordingly increases.Therefore, existing bearing assembly must redesign, to adapt to the turbine loads of such increase.
Therefore it provides improved radial rigidity and/or axial rigidity are to help to adapt to the increasings of modern gas turbine engines
The big bearing assembly radially and/or axially loaded will receive an acclaim in this technique.
Summary of the invention
Aspects and advantages of the present invention will partially elaborate in the following description, or can become from description obviously, or can
Practice and acquistion through the invention.
In an aspect, this theme is related to a kind of bearing assembly, is used for the support relative to gas-turbine unit
Structural support armature spindle.The bearing assembly can generally include bearing and outer bearing outer cover, which includes outer race and inner seat
Circle, the outer bearing outer cover are configured between outer race and the support construction of gas-turbine unit radially.In addition, should
Bearing assembly may include inner bearing supporting element, and the inner bearing supporting element is radial between outer supporting element end and inner support member end
Ground extends, and the outer support part end structure is at configuration near the inside race of bearing, and the inner support member end structure is at rotatable
Ground is connected in armature spindle.The first spring including the inner bearing supporting element may include between outer support part end radially
Arm and second spring arm.The inner bearing supporting element may also include ribs, and the ribs is by first spring arm and second spring arm
It separates, so that first spring arm is from ribs, radially outward supporting element end extends outwardly, and second spring arm is from ribs diameter
Extend to inward towards inner support member end.
In another aspect, this theme is related to a kind of bearing assembly, is used for the support relative to gas-turbine unit
Structural support armature spindle.The bearing assembly can generally include bearing and outer bearing outer cover, which includes outer race and inner seat
Circle, radially from inside and outside cover end and outer cover end, the inside and outside cover end structure is at configuration in axis for the outer bearing outer cover
Near the outer race held, the outer cover end structure is at the support construction for being connected in gas turbine.The outer bearing outer cover may include
The first spring arm and second spring arm extended between inner and outer outer cover end.The outer bearing outer cover may also include reinforcing ring,
The reinforcing ring separates first spring arm and second spring arm, so that first spring arm is prolonged between ribs and outer cover end
It stretches, and second spring arm extends between ribs and inside and outside cover end.In addition, the bearing assembly may include inner bearing support
Part, the inner bearing support configuration between the inside race and armature spindle of bearing radially.
In another aspect, this theme is related to a kind of bearing assembly, is used for the support relative to gas-turbine unit
Structural support armature spindle.The bearing assembly can generally include bearing, outer bearing outer cover and inner bearing supporting element, which includes
Outer race and inside race, the outer bearing outer cover are configured between the outer race of bearing and the support construction of gas-turbine unit
Radially, the inner bearing support configuration between the inside race and armature spindle of bearing radially.In addition, outer shaft
It holds outer cover and inner bearing supporting element respectively includes at least one spring arm radially, so that outer bearing outer cover and inner bearing
Supporting element is collectively form two springs, the two springs are serially linked between support construction and armature spindle.
Technical solution 1: a kind of bearing assembly is used to support rotor relative to the support construction of gas-turbine unit
Axis, the bearing assembly include:
Bearing comprising outer race and inside race；
Outer bearing outer cover is configured between the outer race and the support construction of the gas-turbine unit radial
Ground extends；With
Inner bearing supporting element, between outer supporting element end and inner support member end radially, the outer support
Part end structure is at configuration near the inside race of the bearing, and the inner support member end structure is at being rotatably coupled to
Armature spindle is stated, the inner bearing supporting element includes the first spring arm between the inner and outer supporting element end radially
And second spring arm, the inner bearing supporting element further includes ribs, and the ribs is by the first spring arm and described the
Two spring arms separate, so that the first spring arm radially outward extends towards outer support part end from the ribs, and
The second spring arm extends from ribs radially inward towards the inner support member end.
Technical solution 2: bearing assembly according to technical solution 1, wherein first and second spring arm relative to
The inner and outer supporting element end axially extends so that the ribs and the inner and outer supporting element end axially between
Every.
Technical solution 3: bearing assembly according to technical solution 1, wherein the inner bearing supporting element includes inner bearing
Ring, in outer support part end, the inner bearing collar is configured to couple to the interior of the bearing for the inner bearing collar configuration
Seat ring.
Technical solution 4: bearing assembly according to technical solution 1, wherein the inner bearing supporting element includes installation
Ring, in the inner support member end, the mounting ring is configured to rotatably join via installation seat ring for the mounting ring configuration
It is connected to the armature spindle.
Technical solution 5: according to bearing assembly described in technical solution 4, wherein the mounting ring is radially prolonged using multiple
The pin stretched and be connected in the installation seat ring, the pin is configured to transport through institute when the moment load more than predetermined load threshold values
Destruction when stating axis.
Technical solution 6: according to bearing assembly described in technical solution 4, wherein sliding interface be limited to the mounting ring with
Between the installation seat ring.
Technical solution 7: bearing assembly according to technical solution 1, wherein the outer bearing outer cover is in outer cover end
Between inside and outside cover end radially, the outer cover end structure is at being connected in the support construction, the inside and outside cover
End structure at configuration near the outer race of the bearing, the outer bearing outer cover be included in the inner and outer outer cover end it
Between the first outer cover spring arm and the second outer cover spring arm that extend.
Technical solution 8: according to bearing assembly described in technical solution 7, wherein the outer bearing outer cover further includes reinforcing
Ring, the reinforcing ring separate the first outer cover spring arm and the second outer cover spring arm, so that the first outer cover bullet
Spring arm extends between the reinforcing ring and the outer cover end, and the second outer cover spring arm is in the reinforcing ring and institute
It states and extends between inside and outside cover end.
Technical solution 9: according to bearing assembly described in technical solution 8, wherein the first and second outer covers spring arm phase
The inner and outer outer cover end is axially extended so that the reinforcing ring and the inner and outer outer cover end axially between
Every.
Technical solution 10: according to bearing assembly described in technical solution 7, wherein the outer bearing outer cover includes that installation is convex
Edge, mounting flange configuration in the outer cover end, the outer cover end structure at being connected in the support construction,
And wherein, the outer bearing outer cover includes outer collar bearing, and outer collar bearing configuration is described inside and outside in the inside and outside cover end
Cover end structure is at the outer race for being connected in the bearing.
Technical solution 11: a kind of bearing assembly is used to support rotor relative to the support construction of gas-turbine unit
Axis, the bearing assembly include:
Bearing comprising outer race and inside race；
Outer bearing outer cover, radially from inside and outside cover end and outer cover end, the inside and outside cover end structure at
Configuration near the outer race of the bearing, the outer cover end structure at the support construction for being connected in the gas turbine,
The outer bearing outer cover includes the first spring arm and second spring arm extended between the inner and outer outer cover end, described outer
Bearing outer cover further includes reinforcing ring, and the reinforcing ring separates the first spring arm and the second spring arm, so that described
First spring arm extend between the ribs and the outer cover end and the second spring arm ribs with it is described
Inside and outside cover extends between end；With
Inner bearing supporting element is configured between the inside race and the armature spindle of the bearing radially.
Technical solution 12: according to bearing assembly described in technical solution 11, wherein first and second spring arm is opposite
Axially extend in the inner and outer outer cover end, so that the reinforcing ring is axially spaced with the inner and outer outer cover end.
Technical solution 13: according to bearing assembly described in technical solution 11, wherein the outer bearing outer cover includes that installation is convex
Edge, in the outer cover end, the mounting ring is configured to couple to the support construction for the mounting flange configuration.
Technical solution 14: according to bearing assembly described in technical solution 11, wherein the outer bearing outer cover includes outer bearing
Ring, in the inside and outside cover end, the outer collar bearing is configured to couple to the outer seat of the bearing for the outer collar bearing configuration
Circle.
Technical solution 15: according to bearing assembly described in technical solution 11, wherein the inner bearing supporting element is in outer support
Between part end and inner support member end radially, the outer support part end structure is at the inner seat configured in the bearing
Near circle, the inner support member end structure is included at the armature spindle, the inner bearing supporting element is rotatably coupled to
The first support spring arm and the second support spring arm between the inner and outer supporting element end radially.
Technical solution 16: according to bearing assembly described in technical solution 15, wherein the inner bearing supporting element further includes adding
Strong rib, the ribs separate the first support spring arm and the second support spring arm, so that first support
Spring arm radially outward extends towards outer support part end from the ribs, and the second support spring arm adds from described
Strong rib extends radially inward towards the inner support member end.
Technical solution 17: according to bearing assembly described in technical solution 16, wherein the first and second support springs arm
Axially extend relative to the inner and outer supporting element end, so that the ribs and the inner and outer supporting element end are axial
Ground interval.
Technical solution 18: according to bearing assembly described in technical solution 15, wherein the inner bearing supporting element includes installation
Ring, in the inner support member end, the mounting ring is configured to rotatably join via installation seat ring for the mounting ring configuration
It is connected to the armature spindle.
Technical solution 19: according to bearing assembly described in technical solution 18, wherein the mounting ring using it is multiple radially
The pin of extension and be connected in the installation seat ring, the pin is configured to transport through when more than the moment load of predetermined load threshold value
It is destroyed when the axis.
Technical solution 20: a kind of bearing assembly is used to support rotor relative to the support construction of gas-turbine unit
Axis, the bearing assembly include:
Bearing comprising outer race and inside race；
Outer bearing outer cover, be configured to the bearing outer race and the gas-turbine unit support construction it
Between radially；With
Inner bearing supporting element is configured between the inside race and the armature spindle of the bearing radially,
Wherein, the outer bearing outer cover and the inner bearing supporting element respectively include at least one spring radially
Arm, so that the outer bearing outer cover and the inner bearing supporting element are collectively form and are serially linked in the support construction and institute
State two springs between armature spindle.
Referring to following description and appended claims, these and other features, aspects and advantages of the invention will be managed more preferably
Solution.It is incorporated in this specification and forms part thereof of attached drawing and instantiate the embodiment of the present invention, and be used to solve together with explanation
Release the principle of the present invention.
Detailed description of the invention
The disclosure for being directed to the complete of those skilled in the art and can be realized of the invention, including its preferred forms,
It is illustrated in the specification referring to attached drawing, in the figure:
Fig. 1 illustrates the sectional view of one embodiment of gas-turbine unit, which can be used in basis
In the aircraft of the aspect of this theme；
Fig. 2 illustrates the sectional view of one embodiment of bearing assembly, which is used for respect to this theme
The correspondence support construction of the engine of aspect supports the armature spindle of gas-turbine unit；
Fig. 3 illustrates the partial cross-sectional view of bearing assembly shown in Figure 2, specifically illustrates the outer bearing of bearing assembly
Outer cover；And
Fig. 4 illustrates another partial cross-sectional view of bearing assembly shown in Figure 2, specifically illustrates the interior of bearing assembly
Bearing supports.
List of parts
10 gas-turbine units
12 is axial
14 engines
16 fan sections
18 outer housings
20 annular entrances
22 booster compressors
24 Axial Flow Compressors
26 burners
28 turbines
30 high drive axis
32 low-pressure turbines
34 low-voltage driving axis
37 deceleration devices
38 fan propeller components
40 ring-type fan shells
42 export orientation guide vanes
44 fan rotor blades
46 downstream sections
48 air flow ducts
50 air streams
52 imports
54 arrows
56 air streams
58 arrows
60 combustion products
100 first bearing components
101 second bearing components
102 outer bearing outer covers
104 inner bearing supporting elements
106 armature spindles
108 braced frames
110 sealed compartments
112 bearings
114 inside races
116 outer races
118 rolling elements
120 inside and outside cover ends
122 outer cover ends
124 outer collar bearings
126 flanges
128 bearing surfaces
130 antelabium
134 holes
136 receive bolt
138 first spring arms
140 second spring arms
142 reinforcing rings
144 inner support member ends
146 outer support part ends
148 bearer rings
150 mounting rings
152 bearing surfaces
154 antelabium
156 spanner nuts
158 inner surfaces
160 outsides
162 installation seat rings
164 first spring arms
166 second spring arms
168 ribs
170 safety piece structures
172 mounting pins.
Specific embodiment
Now will be in detail referring to the embodiment of the present invention, one or more example illustrates in the accompanying drawings.Each example
Be as explanation of the invention and the limitation of non-present invention and provide.In fact, will be aobvious to those skilled in the art
And it is clear to, various changes can be carried out in the present invention and is altered without departing from the scope or spirit of the invention.For example, illustrating
Or it is described as the feature of the part of one embodiment and can be used together with another embodiment to generate another embodiment.Therefore, it anticipates
Figure present invention covering falls into such change and change in the range of the appended claims and their equivalents.
By and large, this theme is related to improved bearing assembly, is used to come relative to the correspondence support construction of engine
Support the armature spindle of gas-turbine unit.Specifically, in several embodiments, bearing assembly may include outer bearing outer cover,
Inner bearing supporting element and bearing, bearing are connected between outer bearing outer cover and inner bearing supporting element, so that outer bearing outer cover is from axis
It holds and radially outward extends towards the support construction of engine, and inner bearing supporting element extends from bearing radially inward towards armature spindle.Such as
It will be described below, inner bearing supporting element can have " bipyramid " axis construction, be somebody's turn to do " bipyramid " axis construction by interior bearing supports
Opposite end and inner bearing supporting element corresponding axial ribs between the first and second bullets for radially and axially extending
Spring arm is formed.Spring arm can generally allow for inner bearing supporting element to have relatively low radial rigidity, and axial ribs can mention
For required axial rigidity, for maintaining desired rotor-stator gap.
In addition, as will be described below, outer bearing outer cover may include similar with the construction of inner bearing supporting element " double
Cone " construction.For example, outer bearing outer cover may also comprise the first and second spring arms, first and second spring arm is outside outer bearing
Radially and axially extend between the axial reinforcing ring corresponding with outer cover of the opposite end of cover.As a result, outer bearing outer cover and interior
Bearing supports can generally form two " springs ", the two " springs " join in series between support construction and armature spindle
It connects.Such construction allows the significant decrease of the radial rigidity for disclosed bearing assembly, passes so that component be allowed to reduce
It send to the radial load of other neighbouring engine components.
Referring now to attached drawing, Fig. 1 illustrates the sectional view of one embodiment of gas-turbine unit 10, and gas turbine starts
Machine 10 can be used in the aircraft according to the aspect of this theme, and wherein engine 10, which is shown as having, extends through it for referring to
Longitudinally or axially cener line 12.By and large, engine 10 may include core gas turbine engine (generally by joining
Examine the instruction of label 14) and it is positioned on the fan section 16 of trip.Core-engine 14 can generally include substantially tubular shape
Outer housing 18, the substantially tubular shape outer housing 18 limit annular entrance 20.In addition, outer housing 18 can also be encapsulated and support pressurization
Compressor 22, for the pressure for entering the air of core-engine 14 to be increased to first pressure level.High pressure, multistage, axis
Then streaming compressor 24 can receive the forced air from booster compressor 22, and further increase the pressure of such air.
It leaves the forced air of high temperature compressor 24 and then burner 26 can be flowed to, in burner 26, it is empty that fuel is injected into pressurization
In air-flow, obtained in mixture burn in burner 26.High-energy combustion product is by the hot gas path along engine 10
It is directed to first (high pressure) turbine 28 from burner 26, for driving high pressure compressor via first (high pressure) drive shaft 30
24, and be then channeled to second (low pressure) turbine 32 with for via with substantially coaxial second (low of the first drive shaft 30
Pressure) drive shaft 34 drives booster compressor 22 and fan section 16.Driving turbine 28 and 32 in it is each after, combustion product
It can be discharged via exhaust nozzle 36 from core-engine 14, to provide propulsion jet thrust.
In addition, as shown in fig. 1, the fan section 16 of engine 10 can generally include rotatable, axial-flow type fan
Rotor assembly 38, the fan propeller component 38 are configured to be surrounded by ring-type fan shell 40.It will be understood by those skilled in the art that
Be, blower-casting 40 may be configured to relative to core-engine 14 by it is multiple essentially radially extend, be circumferentially spaced go out
Mouth guiding guide vane 42 supports.In addition, bearing support structure 108 (Fig. 2) can be extended radially inwardly from export orientation guide vane 42.Cause
This, blower-casting 40 can encapsulate fan propeller component 38 and its corresponding fan rotor blade 44.Moreover, under blower-casting 40
Trip section 46 can extend above the outer portion of core-engine 14, so as to limit provide additional propulsion jet thrust pair or
Bypath air flow tube road 48.
It should be understood that in several embodiments, second (low pressure) drive shaft 34 can be coupled directly to fan propeller group
Part 38 directly drives construction to provide.Alternatively, the second drive shaft 34 can be via deceleration device 37 (for example, reduction gearing or tooth
Roller box) it is connected in fan propeller component 38, to provide driving or gear drive configuration indirectly.Such deceleration device can also be according to the phase
Hope or demand and provide between any other in-engine suitable axis and/or shaft.
During the operation of engine 10, it should be appreciated that initial air stream (being indicated by arrow 50) may pass through wind
The relevant inlet 52 for fanning outer cover 40 enters engine 10.Then air stream 50 travels across fan blade 44, and split into first
Compressed air stream (being indicated by arrow 54) and the second compressed air stream (being indicated by arrow 56), first compressed air stream pass through pipe
Road 48 is mobile, which enters booster compressor 22.Then the pressure of second compressed air stream 56 is increased,
And enter high pressure compressor 24 (as indicating arrow 58).After mixing with fuel and burning in burner 26, burning
Product 60 leaves burner 26 and flows through the first turbine 28.Later, combustion product 60 flows through the second turbine 32, and from
The gas jets that begin to rehearse 36, to provide the thrust for being used for engine 10.
Referring now to Fig. 2-4, the axis for being suitable for using in gas-turbine unit 10 is illustrated according to the aspect of this theme
The various sectional views of one embodiment of bearing assembly 100.Specifically, Fig. 2 illustrates the wind relative to gas-turbine unit 10
Fan the sectional view for the bearing assembly 100 that rotor assembly 38 is installed.Fig. 3 illustrates the partial cross section of bearing assembly 100 shown in Figure 2
Figure specifically illustrates the outer bearing outer cover 102 of bearing assembly 100.In addition, Fig. 4 illustrates bearing assembly shown in Figure 2
100 another partial cross-sectional view specifically illustrates the inner bearing supporting element 104 of bearing assembly 100.
As shown in Fig. 2, bearing assembly 38 can generally include armature spindle 106 (for example, axis 34 shown in Fig. 1), rotor
Axis 106 is configured to support (the figure of fan blade 44 of the rotor assembly 38 to extend radially outwardly from corresponding rotor disk (not shown)
1) array.Such as general understanding, armature spindle 106 can pass through one or more bearing assemblies 100,101 being axially spaced
And be supported in engine 10, bearing assembly 100,101 is configured to the structural support frame relative to gas-turbine unit 10
Frame 108 pivotally supports armature spindle 42.For example, as shown in Fig. 2, first bearing component 100 can be axial in second bearing component 101
It is connected at the place at rear between armature spindle 106 and braced frame 108.In several embodiments, first bearing component 100 can
At the second bearing position in engine 10, and it can correspond to fan thrust bearing, and second bearing component 101 can be located at
At first bearing position in engine 10, and it can correspond to roller bearing component.
As shown in embodiment illustrated, 100 (hereinafter referred to simply as bearing assembly of first bearing component
100) annular of engine 10 being limited between armature spindle 106 and braced frame 108, the compartment of sealing can be generally positioned at
In 110.In several embodiments, bearing assembly 100 may include bearing 112, outer bearing outer cover 102 and inner bearing supporting element 104,
Outer bearing outer cover 102 between bearing 112 and braced frame 108 radially, inner bearing supporting element 104 bearing 112 with
Between armature spindle 106 radially.As shown in Fig. 2, bearing 112 can generally include inside race 114, outer race 116 and more
A rolling element 118 (only showing one of those), outer race 116 are radially outwardly positioned from inside race 114, multiple rolling members
Including the configuration of part 118 between outer race 114,116.Rolling element 118 can substantially correspond to any suitable bearing element,
Such as ball or roller.
It should be understood that bearing 112 can generally have allow it to work as described in this article to appoint
What suitable bearing construction.For example, in one embodiment, inside race 114 can have separation block ring structure, so that inside race
114 include both preceding inside race part 114A (Fig. 3) and rear inside race part 114B (Fig. 3).Moreover, in one embodiment,
Other than separating inside race (or as its alternative), outer race 116 can also have separation block ring structure.
As shown in Figures 2 and 3, outer bearing outer cover 102 can be generally in inside and outside cover end 120 (Fig. 3) and outer cover end 122
Between (Fig. 3) radially, wherein outer bearing outer cover 102 includes outer collar bearing 124 and mounting flange 126, outer collar bearing 124
At inside and outside cover end 120, mounting flange 126 is configured in outer cover end for configuration.By and large, outer collar bearing 124 can structure
It causes to dock with the outer seat loop 116 of bearing 112 or is connected in it.For example, outer collar bearing 124 can as specifically illustrated in Fig. 3
Outer circumferential bearing surface 128 is limited, the entire outer periphery contact which is configured about bearing 112 is outer
Seat ring 116 otherwise configures in its vicinity.
In addition, outer collar bearing 124 may include suitable retention feature, or can be associated therewith, for relative to outer bearing
Outer cover 102 axially holds bearing 112.For example, antelabium 130 constructs as shown in figure 3, outer collar bearing 124 may include antelabium 130
Radially at the rear side along outer race 116, so as to prevent bearing 112 relative to outer bearing outer cover 102 axially rearward side
To movement.Moreover, also (multiple) retention feature can be provided along the front side of outer race 116.For example, as shown in figure 3, in a reality
Apply in example, preceding retention feature can correspond to spanner nut (spanner nut) 132, spanner nut 132 via suitable bolt or
Other fasteners are connected in outer collar bearing 124.
As shown in Figures 2 and 3, in several embodiments, outer bearing outer cover 102 can be connected in via mounting flange 126 and start
The braced frame 108 of machine 10, mounting flange 126 configure at the outer cover end 122 of outer cover 102.By and large, mounting flange
126 may be configured to be connected in braced frame 108 using any suitable attachment means.For example, as in embodiment illustrated
Show, mounting flange 126 can limit multiple bolts hole 134 (Fig. 3) (only showing one of those) axially extended, with
In reception bolt 136 or it is configured to for mounting flange 126 to be connected in other suitable fasteners of braced frame 108.At other
In embodiment, outer bearing outer cover 102 may be configured to be connected in braced frame 108 using any other suitable attachment means.
In addition, as shown in Figures 2 and 3, outer bearing outer cover 102 may additionally include the first and second outer cover ends 120,122 it
Between the first and second spring arms 138,140 for extending.Specifically, as shown in figure 3, first spring arm 138 may be configured to from peace
It fills flange 126 radially-inwardly and extends axially forward to the axial reinforcing ring 142 of outer bearing outer cover 102.In addition, second spring arm
140 may be configured to from axial reinforcing ring 142 radially-inwardly and extend axially rearward to outer collar bearing 124.By and large, spring arm
138, it 140 may be configured to that outer bearing outer cover 102 is allowed radially to work as spring like component, to provide outer shaft
Hold the reduction of the radial rigidity of outer cover 102.For example, one of spring arm 138,140 or both may be configured to passing through outer shaft
It holds when outer cover 102 applies radial load and radially deforms, so that outer cover 102 be allowed to adapt to the diameter transmitted across bearing assembly 100
To load.
Moreover, the reinforcing ring 142 being located between the first and second spring arms 138,140 can be generally configured into outer bearing
Outer cover 102 provides the axial rigidity increased.As a result, reinforcing ring 142 can be used for reducing the axial negative in application of outer bearing outer cover 102
Axial deflection when load.As shown in Figures 2 and 3, in one embodiment, spring arm 138,140 may be configured to relative to outer shaft
The inner and outer outer cover end 120,122 for holding outer cover 102 in axial direction extends, so that axial reinforcing ring 142 is located at mounting flange
126 and both outer collar bearings 124 axially front.However, in other embodiments, reinforcing ring 142 can have relative to installation
The suitable axially position of any other of flange 126 and/or outer collar bearing 124.
It should be understood that second spring arm 140 is also configured to external bearing outer cover 102 other than reinforcing ring 142
Additional axial rigidity is provided.Specifically, as shown in figure 3, although second spring arm 140 is in reinforcing ring 142 and outer collar bearing
Slightly extend in radial directions between 124, but spring arm 140 extends mainly directed in the axial direction.Therefore, reinforcing ring 142 and
The combination of two spring arms 140 can be used for external bearing outer cover 102 and provide the axial rigidity increased.
In addition, as shown in Figures 2 and 4, inner bearing supporting element 104 can be generally in inner support member end 144 (Fig. 4) and outer branch
Between support member end 146 (Fig. 4) radially, wherein inner bearing supporting element 104 includes inner bearing collar 148 and interior mounting ring
150, inner bearing collar 148 configures at outer supporting element end 146, and the interior configuration of mounting ring 150 is at inner support member end 144.Greatly
For body, inner bearing collar 148 may be configured to dock with the inside race 114 of bearing 112 and/or be connected in it.For example, such as in Fig. 4
In specifically illustrate, inner bearing collar 148 can limit inner circumferential bearing surface 152, inner circumferential bearing surface 152 is configured about axis
112 entire inner periphery contact is held outer race 114 or otherwise to configure in its vicinity.
In addition, inner bearing collar 148 may include suitable retention feature or can be associated therewith, for relative to inner bearing branch
Support member 104 axially holds bearing 112.For example, antelabium 154 constructs as shown in figure 4, inner bearing collar 148 may include antelabium 154
At along the front side of inside race 114 radially, so as to prevent bearing 112 relative to inner bearing supporting element 104 axially forward
The movement in direction.Moreover, also (multiple) retention feature can be provided along the rear side of inside race 114.For example, as shown in figure 4, at one
In embodiment, rear retention feature can correspond to spanner nut 156, and spanner nut 156 is connected in inner bearing supporting element 104.
As shown in Figures 2 and 4, in several embodiments, may be configured to can via mounting ring 150 for inner bearing supporting element 104
Rotatably it is connected in armature spindle 106, mounting ring 150 configures at the inner support member end 144 of supporting element 104.For example, such as scheming
It is specifically illustrated in 4, mounting ring can limit inner surface 158, and inner surface 158 is configured to 160 pairs of the outside with installation seat ring 162
It connects, installation seat ring 162 is rotatably coupled to armature spindle 106.Specifically, in several embodiments, the interior table of mounting ring 150
Face 158 and the outside 160 for installing seat ring 162 can be set so that sliding interface is limited to mounting ring 150 and peace in terms of profile
It fills between seat ring 162.For example, in one embodiment, the inner surface 158 of mounting ring 150 and the outside 160 of installation seat ring 162
The two can limit matched spherical surface.As will be described below, mountable seat ring 162 can be connected in via pin connection part
Mounting ring 150, the pin connection part are configured to destroy if applying excessive moment load by armature spindle 106, at this point,
The sliding interface being limited between installation seat ring 162 and inner bearing supporting element 104 allows armature spindle 106 to tilt, to adjust it
Rotation center.
In addition, as shown in Figures 2 and 4, inner bearing supporting element 104 may additionally include the first and second supporting element ends 144,
The first and second spring arms 164,166 extended between 146.Specifically, as shown in figure 4, first spring arm 164 may be configured to
It radially-inwardly and is extended axially forward from inner bearing collar 148 to the axial ribs 168 of inner bearing supporting element 104.In addition, second
Spring arm 156 may be configured to from axial ribs 168 radially-inwardly and extend axially rearward to mounting ring 150.By and large, bullet
Spring arm 164,166 may be configured to that inner bearing supporting element 104 is allowed radially to work as spring like component, to mention
For the reduction of the radial rigidity of inner bearing supporting element 104.For example, spring arm 164,166 may be configured to support by inner bearing
Part 104 radially deforms when applying radial load, so that supporting element 104 be allowed to adapt to the radial direction transmitted across bearing assembly 100
Load.
Moreover, the ribs 168 being located between the first and second spring arms 164,166 can be generally configured into inner bearing
Supporting element 104.As a result, ribs 168 can be used for reducing the axial deflection of inner bearing supporting element 104 when applying axial load.
As shown in Figures 2 and 4, in one embodiment, spring arm 164,166 may be configured to the inner and outer branch relative to inner bearing supporting element
Support member end 144,146 in axial direction extends, so that axial ribs 168 is located at both inner bearing collar 148 and mounting ring 150
Axially front.However, in other embodiments, ribs 168 can have relative to inner bearing collar 148 and/or outer mounting ring
150 any other suitable axially position.
It should be understood that due to the construction of outer bearing outer cover 102 and inner bearing supporting element 104, disclosed bearing assembly
100 generally have a dual spring construction, two of them " spring " be serially linked armature spindle 106 and support frame 108 it
Between.Specifically, the group of the spring arm 164,166 of the spring arm 138,140 and inner bearing supporting element 104 of outer bearing outer cover 102
Conjunction allows entire bearing assembly 100 to have relatively low radial rigidity, so that the rotation center of armature spindle 106 is in engine
Uneven event in close to new rotor c.g., to provide the reduced load transmission by component 100.In addition, outer shaft
Required axial rigidity can also be provided in the construction for holding outer cover 102 and inner bearing supporting element 104, for remaining low during load
Axial deflection, so that disclosed bearing assembly 100 be allowed to assist realizing desired (multiple) rotor-stator gaps.
It is to be further understood that as indicated above, bearing assembly 100 may also include suitable load reduction feature or
Can be associated therewith, with the rotation dynamic load for reducing fan support system.Specifically, in several embodiments, outer bearing
The axial reinforcing ring 142 of outer cover 102 may be configured to be connected in the master extended between reinforcing ring 142 and second bearing component 101
Safety piece structure 170 (Fig. 2).As will be described below, main safety piece structure 170 may be configured to apply by structure 170
It is destroyed when excessive radial load.
In addition, as shown in Figure 4, inner bearing supporting element 104 may be configured to be connected in installation seat ring via pin connection part
162.It is limited to specifically, multiple mounting pins 172 may be configured to the edge between interior bearing supports 104 and installation seat ring 162
Interface between such component is radially.In several embodiments, mounting pin 172 can correspond to shear pin, shear pin structure
It causes to be applied to the circumferential interface being limited between inner bearing supporting element 104 and installation seat ring 162 when given shear-loaded
When destroy.
During the operation of gas-turbine unit 10, the imbalance in engine 10 can cause significantly high radial force,
The radial force be applied the fan section 16 across engine 10 and be applied to support rotor assembly 38 bearing assembly 100,
In 101.If radial force is more than given load threshold, main safety piece structure 170 can be destroyed (for example, in neighbouring first axle
It holds at the place of position).Such destroy allows fan to rotate around new rotation axis, thus to change armature spindle 106
Center of gravity and cause bending load on armature spindle 106, this causes to be located at the bearing assembly 100 at second bearing position again
Moment load.The moment load can act on as the shear-loaded in mounting pin 172, and mounting pin 172 is connected in inner bearing supporting element
Between 104 and installation seat ring 162.If moment load is more than reservation threshold, mounting pin 172 can be destroyed, to allow rotor
Axis 106 surrounds the sliding interface for being limited to inner bearing supporting element 104 and installing between seat ring 162 and tilts, so that in the rotation of axis
The heart is further to new rotor c.g..
This written explanation discloses the present invention, including preferred forms using example, and also makes any this field skill
Art personnel can practice the present invention, including manufacture and use any device or system, and execute any combined method.This hair
Bright patentable scope is defined by the claims, and may include other examples expected by those skilled in the art.
If other such examples include structural details not different from the literal language of claim, or if other such examples
Equivalent structural elements including the literal language with claim without marked difference, then other such examples are intended in claim
In the range of.
Claims (10)
1. a kind of bearing assembly, the support construction for being connected in gas-turbine unit is used to support armature spindle, the bearing group
Part includes:
Bearing comprising outer race and inside race；
Outer bearing outer cover is configured between the outer race and the support construction of the gas-turbine unit radially prolong
It stretches；With
Inner bearing supporting element, between outer supporting element end and inner support member end radially, outer support part end
Cage structure is at configuration near the inside race of the bearing, and the inner support member end structure is at being rotatably coupled to described turn
Sub- axis, the inner bearing supporting element include between the inner bearing supporting element and outer support part end radially first
Spring arm and second spring arm, the inner bearing supporting element further includes ribs, the ribs by the first spring arm with
The second spring arm separates, so that the first spring arm is radially outward prolonged towards outer support part end from the ribs
It stretches, and the second spring arm extends from ribs radially inward towards the inner support member end.
2. bearing assembly according to claim 1, wherein the first spring arm and second spring arm are relative to described interior
Bearing supports and outer support part end axially extend, so that the ribs and the inner bearing supporting element and outer support part
End is axially spaced.
3. bearing assembly according to claim 1, wherein the inner bearing supporting element includes inner bearing collar, the inner shaft
Carrier ring is configured in outer support part end, and the inner bearing collar is configured to couple to the inside race of the bearing.
4. bearing assembly according to claim 1, wherein the inner bearing supporting element includes mounting ring, the mounting ring
In the inner support member end, the mounting ring is configured to rotatably be connected in the rotor via installation seat ring for configuration
Axis.
5. bearing assembly according to claim 4, wherein the mounting ring is coupled using multiple pins radially
In the installation seat ring, the pin is configured to broken when the moment load for being more than predetermined load threshold values transports through the armature spindle
It is bad.
6. bearing assembly according to claim 4, wherein sliding interface is limited to the mounting ring and the installation seat ring
Between.
7. bearing assembly according to claim 1, wherein the outer bearing outer cover is in outer cover end and inside and outside cover end
Between radially, the outer cover end structure is at being connected in the support construction, and the inside and outside cover end structure is at matching
It sets near the outer race of the bearing, the outer bearing outer cover, which is included between the inside and outside cover end and outer cover end, to be prolonged
The the first outer cover spring arm and the second outer cover spring arm stretched.
8. bearing assembly according to claim 7, wherein the outer bearing outer cover further includes reinforcing ring, the reinforcing ring
The first outer cover spring arm and the second outer cover spring arm are separated, so that the first outer cover spring arm is in the reinforcement
Extend between ring and the outer cover end, and the second outer cover spring arm the reinforcing ring and the inside and outside cover end it
Between extend.
9. bearing assembly according to claim 8, wherein the first outer cover spring arm and the second outer cover spring arm are opposite
Axially extend in the inside and outside cover end and outer cover end, so that the reinforcing ring and the inside and outside cover end and outer cover
End is axially spaced.
10. bearing assembly according to claim 7, wherein the outer bearing outer cover includes mounting flange, and the installation is convex
Edge configuration is in the outer cover end, and the outer cover end structure is at being connected in the support construction, and wherein, described outer
Bearing outer cover includes outer collar bearing, outer collar bearing configuration in the inside and outside cover end, the inside and outside cover end structure at
It is connected in the outer race of the bearing.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IN3524CH2015 | 2015-07-09 | ||
| IN3524/CHE/2015 | 2015-07-09 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106337739A CN106337739A (en) | 2017-01-18 |
| CN106337739B true CN106337739B (en) | 2019-10-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610535029.9A Active CN106337739B (en) | 2015-07-09 | 2016-07-08 | It is used to support the bearing assembly of the armature spindle of gas-turbine unit |
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|---|---|
| US (1) | US9909451B2 (en) |
| EP (1) | EP3115551A1 (en) |
| JP (1) | JP6183978B2 (en) |
| CN (1) | CN106337739B (en) |
| BR (1) | BR102016015947A2 (en) |
| CA (1) | CA2934668C (en) |
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- 2016-07-01 JP JP2016131189A patent/JP6183978B2/en not_active Expired - Fee Related
- 2016-07-08 EP EP16178645.4A patent/EP3115551A1/en not_active Withdrawn
- 2016-07-08 BR BR102016015947A patent/BR102016015947A2/en not_active Application Discontinuation
- 2016-07-08 CN CN201610535029.9A patent/CN106337739B/en active Active
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Also Published As
| Publication number | Publication date |
|---|---|
| CN106337739A (en) | 2017-01-18 |
| JP6183978B2 (en) | 2017-08-23 |
| CA2934668A1 (en) | 2017-01-09 |
| EP3115551A1 (en) | 2017-01-11 |
| US20170009603A1 (en) | 2017-01-12 |
| BR102016015947A2 (en) | 2017-01-24 |
| JP2017053342A (en) | 2017-03-16 |
| CA2934668C (en) | 2018-11-06 |
| US9909451B2 (en) | 2018-03-06 |
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